JPH11281328A - Method of creating structure analysis model of wing and structure analyzing method and apparatus - Google Patents

Abstract

PROBLEM TO BE SOLVED: To create a three-dimensional structure analysis model of an actual wing by dividing a line passing measuring points between the front and rear edges of each measuring section into a fixed number of segments, and extending lines passing corresponding division points of each measuring section to defined planes. SOLUTION: About a plurality of measuring sections of an actual wing, the positions of a plurality of measuring points are acquired as measuring data, defined sections are set to the end and socket of the wing, and the front and rear end edge of the winding are detected each measuring section, based on the measuring data. About each measuring section, the line passing the measuring points between the front and rear end edges is divided into a fixed number of segments to create division points, and a line passing corresponding division points of each measuring section is extended to each defined plane to create a three-dimensional structure analysis model of the actual wing. This enables the direct structure analysis of the wing and allows the omission of the performance test in the design/development of a wing.

Description

DETAILED DESCRIPTION OF THE INVENTION

[0001]

BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a method for generating a structural analysis model of a blade and a method and an apparatus for structural analysis, and more particularly to an invention suitable for use in structural analysis of blades constituting various engines.

[0002]

2. Description of the Related Art As is well known, blades used in various engines (turbines, compressors, etc.) are relatively thin structures. In the conventional structural analysis of such a blade, a procedure is adopted in which the steady-state stress and deformation of the blade are analyzed based on design parameters such as material and shape, and the analysis result is confirmed by a vibration test or the like. I have. That is, the conventional structural analysis of the wing
Since it is based on design parameters and not based on a real wing, it was not necessarily provided with sufficient accuracy.

On the other hand, when analyzing the structure of a wing, the three-dimensional shape of the actual wing is measured for a plurality of measurement cross sections using a three-dimensional shape measuring instrument, and the measured data of the three-dimensional shape and the material of the material constituting the wing are measured. A method of performing a structural analysis based on material characteristics or the like can be considered. However, there is no conventional three-dimensional shape measuring instrument that outputs measurement data in each measurement section as electronic data. Therefore, a computer or the like directly uses the measurement data of the three-dimensional shape measuring instrument to perform a structural analysis model of the blade. (Wing surface model) could not be created. In order to create a structural analysis model of the wing, the structural analysis operator had to edit the measurement data by himself. Under the circumstances described above, a technique for automatically analyzing a structural analysis of a wing based on three-dimensional measurement data of a real wing actually mounted on the engine has not been realized.

[0004] The present invention has been made in view of the above-mentioned problems, and has the following objects. The structural analysis of the wing is performed based on the actual wing. Structural analysis of the wing is performed directly based on the three-dimensional shape measurement data of the actual wing. Perform more accurate wing structural analysis. Eliminate performance tests in wing design and development. Reduce the cost of equipment that uses wings as part of its structure. To shorten the development period of equipment whose wing is part of the structure.

[0005]

In order to achieve the above object, according to the present invention, as a means related to a method for generating a structural analysis model of a wing, the position of a plurality of measurement points on a plurality of measurement cross sections of a real wing is measured. A process of obtaining as
A step of setting a defined section at each of the tip and the receptacle of the body wing, a step of detecting a leading edge edge and a trailing edge of the body wing at each measurement section based on the measurement data, Generating a plurality of division points by dividing a line connecting each measurement point between the leading edge edge portion and the rear edge edge portion into a predetermined number, and connecting the corresponding division points of the respective measurement cross sections with each other. Generating a three-dimensional structural analysis model of the real wing by extending a line connecting the division points to each of the definition planes.

On the other hand, according to the present invention, as means relating to a wing structure analysis method, a step of generating a three-dimensional structural analysis model of a real wing based on measurement data of a three-dimensional shape of the real wing, Reading the three-dimensional structural analysis model of the support base, the shape of which has been standardized in advance, from the storage means and coupling the three-dimensional structural analysis model to the three-dimensional structural analysis model of the real wing, and the three-dimensional structural analysis model obtained as a result of the coupling And a step of performing a structural analysis.

Further, according to the present invention, as a first means relating to a wing structure analyzing apparatus, a three-dimensional shape measuring apparatus for measuring a three-dimensional shape of a real wing and outputting it as measurement data, and a real body based on the measured data. An arithmetic unit for generating a three-dimensional structural analysis model of a wing and performing a structural analysis of a real wing based on the three-dimensional structural analysis model, and an input device for inputting information necessary for generating the three-dimensional structural analysis model to the arithmetic unit Means for outputting the result of the structural analysis of the actual wing in the arithmetic unit.

[0008] Further, as a second means relating to the wing structure analyzing apparatus, in the above-mentioned first means, an actual wing on a support base whose shape has been standardized in advance based on an actual support structure is used as a support base. A storage device for storing the three-dimensional structural analysis model of the support in advance, and the arithmetic unit combines the three-dimensional structural analysis model of the support wing read from the storage device with the three-dimensional structural analysis model of the actual wing to generate a structure. A means of performing analysis is adopted.

[0009]

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, an embodiment of a method for generating a structural analysis model of a blade, a method and an apparatus for structural analysis according to the present invention will be described with reference to the drawings.

FIG. 1 is a plan view of a structural analysis object according to the present embodiment. In this figure, reference numeral A denotes a real wing actually constituting various engines, and has a three-dimensional shape. In the present embodiment, a real wing A is configured on a support B whose shape has been standardized in advance for structural analysis, and this is set as an object of three-dimensional structural analysis. This support B is
The shape is set based on a support structure of an engine or the like on which the actual wing A is actually mounted. As for the support structure of the actual wing A, the representative shapes are classified into several types.
The real wing A of the present embodiment is configured on a support B whose shape is standardized in advance according to this classification.

FIG. 2 is a functional block diagram of a structural analysis device for performing a structural analysis of the actual wing A. In this figure, reference numeral 1 denotes a three-dimensional shape measuring device for measuring the three-dimensional shape of the actual wing A. The three-dimensional shape measuring apparatus 1 contacts the tip of the inspection probe with the surface of the wing A along a plurality of measurement cross sections d (see FIG. 1) which are set in a ring-shape to form the wing A, The surface shape (three-dimensional shape) is measured.

Instead of such a contact type three-dimensional shape measuring apparatus 1, a laser beam is irradiated along the measurement section d, and the three-dimensional shape of the actual wing A is measured based on the reflected light. It is also possible to use a non-contact type three-dimensional measuring device.

Reference numeral 2 denotes an arithmetic unit, which is a kind of computer that operates based on a structural analysis program. The arithmetic unit 2 performs a process as described below on the three-dimensional shape data measured by the three-dimensional shape measuring device 1 to obtain a structural analysis model (wing surface structure model) of the actual wing A. Generated and numerically analyzed vibration characteristics, steady-state stress characteristics, etc. of the actual blade A based on the structural analysis model.

Reference numeral 3 denotes a storage device for storing the structural analysis program and a plurality of types of structural analysis models of the support B whose shape has been standardized in advance. The storage device 3 also stores data necessary for various types of arithmetic processing in the arithmetic device 2, data input from the input device 4, and the like. The input device 4 is provided for inputting dimensions and the like of the support B.

Reference numeral 5 denotes a display device, which displays the structural analysis model as a three-dimensional image, or displays the actual wing A
For numerically displaying the vibration characteristics, steady stress characteristics, etc. Reference numeral 6 denotes a printing device for printing a structural analysis model as a three-dimensional image or a structural analysis result such as a vibration characteristic and a steady stress characteristic of the actual wing A. Note that the display device 5 and the printing device 6 constitute output means of the present embodiment.

Next, a method of analyzing the structure of the actual wing A will be described with reference to the flowchart shown in FIG. In analyzing the structure of the actual wing A, the three-dimensional shape measuring device 1 measures the three-dimensional shape of the actual wing A in its own coordinate system, and the shape data is taken into the arithmetic device 2. Then, the following processing is performed by the arithmetic unit 2 to perform a structural analysis.

FIG. 4 shows shape data on a certain measurement section d on XY coordinates. The shape data includes a plurality of measurement points p set on each measurement section d.
i (subscript indicating the measurement number) is the three-dimensional coordinate data (coordinate data in the coordinate system of the three-dimensional shape measuring apparatus 1),
It is input to the arithmetic unit 2 together with the measurement number i assigned to the measurement point for each measurement section d.

The arithmetic unit 2 converts such shape data into shape data (actual shape data) based on a coordinate system when the real wing A is actually assembled to the engine (step S1). Thereafter, various processes are performed based on the actual shape data. In this figure, the intervals between the measurement points pi are shown relatively coarsely for the sake of explanation, but are actually set more densely.

The storage device 3 previously stores data relating to the actual engine coordinate system (overall coordinate system). The arithmetic unit 2 converts the shape data into actual shape data based on the data related to the entire coordinate system and the information related to the coordinate system (local coordinate system) of the three-dimensional shape measuring device 1 specified by the input device 4. . Then, the actual shape data is stored in the storage device 3 as a file.

Subsequently, editing of the analysis parameters is performed (step S2). Here, for example, as one of the analysis parameters, the number of divisions of the real wing A in the structural analysis model (the number of divisions in the span direction and the number of divisions in the code direction) is appropriately set by being input from the input device 4. Here, the span direction is the length direction of the actual wing A as shown in FIG. 1, and the cord direction is a direction orthogonal to the span direction.

The TIP-defined section d _T located at the TIP (tip) of the body wing A and the HUB-defined section d _H located at the HUB (reception port) are defined by operating the input device 4 (step S3). . Editing information at step S2 and step S3, that is the division number and the TIP definitions section d _T and HUB defined cross section d _H of division number and code direction in the span direction, the file name and the same file in the file of the actual shape data The name is stored in the storage device 3 (step S4).

The above-described steps S1 to S4 are performed by the analysis operator inputting predetermined information from the input device 4. The processing of steps S5 to S15 described below is processing automatically performed by the arithmetic unit 2 based on the information stored in the storage device 3 by the processing of steps S1 to S4 and the structure analysis program.

First, the arithmetic unit 2 reads out the actual shape data from the storage device 3 to detect the number of the measurement cross sections d (step S5), and furthermore, the measurement points pi in each measurement cross section d.
Is detected (step S6). Then, the folded portion of the measurement point pi in each measurement section d, that is, the edge portion (the leading edge portion and the trailing edge portion: see FIG. 4) of the actual wing A is detected (step S7).

In this embodiment, when performing a structural analysis,
Since the edge does not affect the structural analysis, it is not necessary to include the edge in the structural analysis model. The folded part is detected from the actual shape data, and the edge is excluded from the following structural analysis model generation processing. Here, FIG. 5 is an enlarged view of the folded portion corresponding to the trailing edge portion. As shown in this figure, the arithmetic unit 2 detects an arc-shaped portion as a folded portion based on the actual shape data of each measurement point pi (Step S).
8).

Then, a measurement point pe1 closest to the entrance of the turn-back portion and a measurement point pe2 closest to the exit are detected. Although not shown, the measurement point pe3 closest to the entrance and the measurement point pe4 closest to the exit are similarly detected for the folded portion corresponding to the leading edge.

The arithmetic unit 2 corrects the measurement point and detects the measurement number i for the turn-back portion detected in this way. That is, the arithmetic unit 2 moves the detected measurement points pe1, pe2, pe3, and pe4 to the entrance and the exit of each of the folded portions. Then, by dividing the line generated by connecting the measurement points pi for each measurement section d in the code direction of the actual wing A based on the division number in the code direction, a plurality of division points are formed on each measurement section d. It is generated (step S9).

In this case, the measurement point included between the measurement point pe1 and the measurement point pe2 and the measurement point included between the measurement point pe3 and the measurement point pe4 are ignored. And the trailing edge are excluded from the structural analysis model. The measurement points are corrected at the measurement points pe1 and pe2 so as to minimize the edge parts (leading edge part and trailing edge part) excluded from the structural analysis model.
May be moved.

Furthermore, computing device 2, to extend the dividing points of each measurement section d to HUB defined cross section d _H tie spanwise obtains the intersection as a dividing point of the HUB definition section d _H (step S10), and The division point of each measurement section d is connected in the span direction to extend to the TIP definition section d _T , and the intersection is defined as T
Determined as the division points of the IP definitions section d _T (step S1
1).

The HUB-defined section d _H and the TIP-defined section d _T obtained as described above, and other measurement sections d other than the above.
Are connected by a line in the span direction of the actual wing A, and the line is divided based on the number of divisions in the span direction, so that the nodes (coordinates) of the structural analysis model on the wing surface of the actual wing A ) Is generated (step S12). FIG. 6 is a three-dimensional structural analysis model of the real wing A defined by the nodes thus generated.

Then, the arithmetic unit 2 connects the structural analysis model of the support B to the structural analysis model of the actual wing A configured as described above. In the present embodiment, the support B
Are standardized in advance based on the actual support structure of the actual wing A in an engine or the like. When the analysis operator inputs the dimensions of the support B from the input device 4, the arithmetic unit 2 specifies the shape of the support B based on the input information and stores the structural analysis model corresponding to the support B in the storage device. 3 and connected to the HUB side of the structural analysis model of the actual wing A. With the above processing, a three-dimensional structural analysis model of the real wing A configured on the support B is completed.

In step S14, a structural analysis is performed on the three-dimensional structural analysis model of the actual wing A. In this case, the arithmetic unit 2 analyzes the vibration characteristics or the stress distribution of the three-dimensional structural analysis model according to a well-known analysis processing program for performing modal analysis or static analysis. Then, these analysis results are output to the display device 5 or the printing device 6 (step S14).

As described above, according to the present embodiment, a three-dimensional structural analysis model can be generated almost automatically based on the measurement data of the actual wing A measured by the three-dimensional shape measuring apparatus 1. Further, since the three-dimensional structural analysis model of the support base B is stored in the storage device 3 in advance based on the support structure of the engine or the like to which the actual wing A is actually mounted, the actual support structure of the actual wing A is The three-dimensional structure analysis including the above can be accurately performed in a short time.

[0033]

As described above, according to the blade structural analysis model generating method and the structural analysis method and apparatus according to the present invention, the following effects can be obtained. (1) A three-dimensional shape measuring device that measures the three-dimensional shape of a real wing and outputs the measured data as measurement data, and generates a three-dimensional structural analysis model of the real wing based on the measurement data, based on the three-dimensional structural analysis model An arithmetic unit for performing structural analysis of the actual wing, an input device for inputting information necessary for generating a three-dimensional structural analysis model to the arithmetic device, and an output unit for outputting a result of the structural analysis of the actual wing in the arithmetic device. With this configuration, the structural analysis of the wing can be directly performed based on the measurement data of the three-dimensional shape of the actual wing. Therefore, it is possible to omit the performance test in the design and development of the wing, so that it is possible to reduce the cost of the equipment having the wing as a part of the structure and to shorten the development period of the equipment. (2) A storage device for storing in advance a three-dimensional structural analysis model of the support table for a real wing on the support table whose shape is standardized in advance based on the actual support structure, and the support table read from the storage device The arithmetic unit is configured to perform the structural analysis by combining the three-dimensional structural analysis model of the above and the three-dimensional structural analysis model of the real wing generated by itself, so that a more accurate wing structural analysis can be performed. In addition, by storing the three-dimensional structural analysis model of the support base in a storage device in advance, a three-dimensional structural analysis model can be easily obtained, so that the structure of the actual wing can be analyzed in a short time.

[Brief description of the drawings]

FIG. 1 is a plan view showing a configuration of a structural analysis object according to an embodiment of the present invention.

FIG. 2 is a block diagram illustrating a functional configuration of a wing structure analysis apparatus according to an embodiment of the present invention.

FIG. 3 is a flowchart showing a procedure for analyzing the structure of a wing according to an embodiment of the present invention.

FIG. 4 is a plan view showing a two-dimensional shape of a real wing in a measurement section in one embodiment of the present invention.

FIG. 5 is an explanatory diagram illustrating a correction process of a measurement point according to an embodiment of the present invention.

FIG. 6 is a diagram showing a three-dimensional structural analysis model of a real wing in one embodiment of the present invention.

[Explanation of symbols]

A ...... entity blade B ...... support base d ...... measurement section d _T ...... TIP defined cross section d _H ...... HUB define sectional pi ...... Measurement Point 1 ...... three-dimensional shape measurement apparatus 2 ...... arithmetic device 3 ...... Storage device 4 ... Input device 5 ... Display device (output means) 6 ... Printing device (output means)

Claims (4)

[Claims] 1. A step of acquiring, as measurement data, positions of a plurality of measurement points for a plurality of measurement sections of a body wing, a step of setting a defined section at a tip and a reception port of the body wing, respectively, based on the measurement data. Detecting the leading edge and the trailing edge of the actual wing in each measurement section, and for each measurement section, a line connecting each measurement point between the leading edge and the trailing edge. Generating a plurality of division points by dividing into a predetermined number, connecting the corresponding division points of the respective measurement cross sections, and extending a line connecting the division points to each of the definition surfaces to form a three-dimensional structure of the real wing. A method for generating a structural analysis model of a wing, comprising: generating an analysis model. 2. A step of generating a three-dimensional structural analysis model of the real wing based on measurement data of the three-dimensional shape of the real wing, and a three-dimensional shape of the support base whose shape is standardized in advance based on the actual support structure. Reading a structural analysis model from the storage means and coupling the structural analysis model to the three-dimensional structural analysis model of the physical wing; and performing a structural analysis of the three-dimensional structural analysis model obtained as a result of the coupling. To analyze the structure of the wing. 3. A three-dimensional shape measuring device that measures a three-dimensional shape of a real wing and outputs the measured data as measurement data, and generates a three-dimensional structural analysis model of the real wing based on the measurement data. Computing device for performing a structural analysis of a body wing based on a computer, an input device for inputting information necessary for generating a three-dimensional structural analysis model to the computing device, and an output unit for outputting a result of the structural analysis of the body wing in the computing device A structural analysis device for a wing, comprising: 4. A storage device for storing in advance a three-dimensional structural analysis model of a support base for a real wing on a support base whose shape has been standardized in advance based on an actual support structure, 4. The wing structure analyzing apparatus according to claim 3, wherein the structural analysis is performed by combining the three-dimensional structural analysis model of the support base read out from the apparatus and the three-dimensional structural analysis model of the real wing generated by itself.